EP2060759B1 - Gasturbine mit zwei Nebenaggregategetriebe - Google Patents
Gasturbine mit zwei Nebenaggregategetriebe Download PDFInfo
- Publication number
- EP2060759B1 EP2060759B1 EP08253726.7A EP08253726A EP2060759B1 EP 2060759 B1 EP2060759 B1 EP 2060759B1 EP 08253726 A EP08253726 A EP 08253726A EP 2060759 B1 EP2060759 B1 EP 2060759B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- accessory drive
- core
- fan
- nacelle
- gearboxes
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Revoked
Links
- 239000000446 fuel Substances 0.000 claims description 7
- 238000005461 lubrication Methods 0.000 claims description 4
- 239000007858 starting material Substances 0.000 claims description 4
- 238000011144 upstream manufacturing Methods 0.000 claims description 2
- 238000004806 packaging method and process Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/32—Arrangement, mounting, or driving, of auxiliaries
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/40—Use of a multiplicity of similar components
Definitions
- This disclosure relates to a gas turbine gearbox arrangement that is used to support and rotationally drive accessory drive components, such as a fuel pump, hydraulic pump, generator, lubrication pump and/or starter.
- accessory drive components such as a fuel pump, hydraulic pump, generator, lubrication pump and/or starter.
- Gas turbine engines for commercial aircraft applications typically include an engine core housed within a core nacelle.
- the core drives a large fan upstream from the core that provides airflow into the core.
- One or more spools are arranged within the core, and a gear train may be provided between one of the spools and the fan.
- a fan case and nacelle surround the fan and at least a portion of the core.
- An inlet of the fan nacelle is designed to avoid flow separation. At cruise conditions, a thinner inlet lip is desired to minimize drag and increase fuel economy.
- the nacelles are sized to accommodate the widest section of engine, which is often dictated by the size of a single accessory drive gearbox.
- the accessory drive gearbox which is driven by a spool through a radial tower shaft and angle gearbox, is typically contained within either the fan nacelle or the core nacelle.
- a fuel pump, hydraulic pump, generator, lubrication pump, starter and numerous other components are typically mounted to the same accessory drive gearbox, which takes up significant space.
- the diameter of the nacelle housing the accessory drive gearbox and accessory components must be increased beyond a desired size.
- the larger diameter nacelle results in a thicker inlet lip thereby increasing drag at cruise conditions. Increased nacelle diameter also increases weight and fuel consumption. What is needed is a gas turbine engine design with a reduced diameter nacelle.
- Gas turbine engines having multiple gearboxes rotationally coupled to at least one spool of the engine are disclosed in WO 95/02120 A1 and WO 2005/005810 A1 .
- the present invention provides a gas turbine engine as set forth in claim 1.
- the accessory drive components are split between the two gearboxes to reduce the diameter of the nacelle adjacent to each gearbox, enabling the design of slimmer nacelles and more efficient engines.
- FIG. 1 An engine 10 with geared architecture is shown in Figure 1 .
- a pylon secures the engine 10 to an aircraft.
- the engine 10 includes a core nacelle 12 that surrounds a low spool 14 and high spool 24 that are rotatable about a common axis A.
- the low spool 14 supports a low pressure compressor 16 and low pressure turbine 18.
- the low spool 14 drives a fan 20 through a gear train 22.
- the high spool 24 supports a high pressure compressor 26 and high pressure turbine 28.
- a combustor 30 is arranged between the high pressure compressor 26 and high pressure turbine 28. Compressed air from compressors 16, 26 mixes with fuel from the combustor 30 and is expanded in turbines 18, 28.
- the engine 10 is a high bypass turbofan arrangement.
- the bypass ratio is greater than 10
- the turbofan diameter is substantially larger than the diameter of the low pressure compressor 16.
- the low pressure turbine 18 has a pressure ratio that is greater than 5:1, in one example.
- the gear train 22 is an epicycle gear train, for example, a star gear train, providing a gear reduction ratio of greater than 2.5:1. It should be understood, however, that the above parameters are only exemplary of a contemplated geared architecture engine. That is, the invention is applicable to other engines including direct drive turbofans.
- the fan 20 directs air into the core nacelle 12, which is used to drive the turbines 18, 28, as is known in the art.
- Turbine exhaust exits the core nacelle 12 once it has been expanded in the turbines 18, 28, in a passage provided between the core nacelle 12 and a tail cone 32.
- a core housing 11 is arranged within the core nacelle 12 and is supported within the fan nacelle 34 by structure 36, such as flow exit guide vanes, extending radially inwardly from a fan case 35.
- structure 36 such as flow exit guide vanes, extending radially inwardly from a fan case 35.
- a generally annular bypass flow path 38 is arranged between the core and fan nacelles 12, 34.
- the examples illustrated in the Figures depict a high bypass flow arrangement in which approximately eighty percent of the airflow entering the fan nacelle 34 bypasses the core nacelle 12.
- the bypass flow within the bypass flow path 38 exits the fan nacelle 34 through a fan nozzle exit area at the aft of the fan nacelle 34.
- At least two accessory drive gearboxes 40, 140 are used to drive accessory components at different location within the engine.
- the work can be split between the gearboxes 40, 140 to reduce the size of each gearbox and, thus, the size of the associated nacelle.
- Example accessory drive components are: a fuel pump 42, hydraulic pump 44, generator 46, lubrication pump 48, starter 50 and other accessory drive components 53.
- one accessory drive gearbox 40 is arranged in a radial space between the fan case 35 and an exterior surface 33 of the fan nacelle 34.
- the other accessory drive gearbox 140 is arranged in a radial space between the core housing 11 and an exterior surface 13 of the core nacelle 12.
- the accessory drive gearboxes are axially and radially spaced from one another, which enables desired packaging of the gearboxes.
- the accessory drive gearbox 40 is driven by the low spool 14.
- the low spool 14 is coupled to a tower shaft 62 with bevel gears, as is known.
- the tower shaft 62 drives an input shaft 52 through an angle gearbox 64, which is mounted to the fan case 35, for example.
- the accessory drive gearbox 40 is supported by the fan case 35, and receives rotational drive from the input shaft 52.
- the accessory components shown mounted on the accessory drive gearboxes 40, 140 are exemplary only and may be different than depicted in the Figures.
- the accessory components for each gearbox are selected, for example, based upon packaging considerations and the desired rotational speed of the accessory component.
- the accessory drive gearboxes 40, 140 are respectively driven by the low and high spools 14, 24 to provide the desired rotational speed to accessory drive components associated with the gearboxes.
- the accessory drive gearbox 140 is driven by the high spool 24.
- the high spool 24 is coupled to a tower shaft 162 with bevel gears.
- the tower shaft 162 drives an input shaft 152 through an angle gearbox 164, which is mounted to the core housing 11, for example.
- the accessory drive gearbox 140 is supported by the core housing 11, and receives rotational drive from the input shaft 152.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Retarders (AREA)
- Other Liquid Machine Or Engine Such As Wave Power Use (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- General Details Of Gearings (AREA)
Claims (4)
- Turbinenmotor (10), umfassend:ein erstes und ein zweites Nebenaggregatgetriebe (40, 140), die an mindestens eine Spule (14, 24) drehgekoppelt sind, die niedrige und hohe, um eine gemeinsame Achse (A) drehbare Spulen (14, 24) umfasst, wobei das erste und zweite Nebenaggregatgetriebe (40, 140) jeweils an die niedrigen und hohen Spulen (14, 24) drehgekoppelt sind;Kern- und Lüftungsgondeln (12, 34), wobei die Kerngondel (12) die mindestens eine Spule (14, 24) und die Lüftungsgondel (34) die Kerngondel (12) umgibt, um einen Bypass-Strömungsweg zwischen den Gondeln (12, 34) und den Nebenaggregatgetrieben (40, 140) zu schaffen;ein Lüftungsgehäuse (35), das eine Lüftung (20) umgibt, die der Kerngondel (12) vorgelagert ist, und ein Kerngehäuse (11), das um die mindestens eine Spule (14, 24) angeordnet ist, wobei die Nebenaggregatgetriebe (40, 140) von mindestens einem von dem Lüftungsgehäuse (35) und dem Kerngehäuse (11) getragen werden, und die Kerngondel (12) von dem Kerngehäuse (11) radial nach außen angeordnet ist, wodurch ein erster radialer Raum dazwischen geschaffen wird, und die Lüftungsgondel (34) von dem Lüftungsgehäuse (35) radial nach außen angeordnet ist, wodurch ein zweiter radialer Raum dazwischen geschaffen wird;Nebenaggregatgetriebeelemente, einschließlich mindestens zwei der Folgenden: einer Treibstoffpumpe (42), eines Generators (46), einer Schmierpumpe (48) oder eines Anlassers (50); undwobei eines der Nebenaggregatgetriebeelemente an dem ersten Nebenaggregatgetriebe (40) befestigt ist und von diesem angetrieben wird, und ein anderes der Nebenaggregatgetriebeelemente an dem zweiten Nebenaggregatgetriebe (140) befestigt ist und von diesem angetrieben wird, wobei das erste und zweite Nebenaggregatgetriebe (40, 140) jeweils in dem ersten und zweiten radiale Raum angeordnet sind.
- Turbinenmotor nach Anspruch 1, wobei die Kern- und Lüftungsgondeln (12, 34) jeweils äußere Oberflächen (13, 33) aufweisen, wobei die Nebenaggregatgetriebe (40, 140) und ihre jeweiligen Nebenaggregatgetriebeelemente (42 ...50) radial innerhalb der äußeren Oberflächen (13, 33) enthalten sind.
- Turbinenmotor nach einem der vorangehenden Ansprüche, wobei das erste und zweite Nebenaggregatgetriebe (40, 140) axial voneinander beabstandet sind.
- Turbinenmotor nach einem der vorangehenden Ansprüche, wobei mindestens eines der Nebenaggregatgetriebe (40, 140) an die mindestens eine Spule (14, 24) durch eine Turmwelle (62, 162), ein Winkelgetriebe (64, 164) und eine Eingangswelle (52, 152) gekoppelt ist, wobei das Winkelgetriebe (64, 164) zwischen den Turm- (62, 162) und Eingangswellen (64, 164) eingebunden ist.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/939,725 US8333554B2 (en) | 2007-11-14 | 2007-11-14 | Split gearbox and nacelle arrangement |
Publications (3)
Publication Number | Publication Date |
---|---|
EP2060759A2 EP2060759A2 (de) | 2009-05-20 |
EP2060759A3 EP2060759A3 (de) | 2012-03-21 |
EP2060759B1 true EP2060759B1 (de) | 2016-01-27 |
Family
ID=40276098
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP08253726.7A Revoked EP2060759B1 (de) | 2007-11-14 | 2008-11-14 | Gasturbine mit zwei Nebenaggregategetriebe |
Country Status (2)
Country | Link |
---|---|
US (1) | US8333554B2 (de) |
EP (1) | EP2060759B1 (de) |
Families Citing this family (28)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9719428B2 (en) * | 2007-11-30 | 2017-08-01 | United Technologies Corporation | Gas turbine engine with pylon mounted accessory drive |
US20100192595A1 (en) | 2009-01-30 | 2010-08-05 | Robert Joseph Orlando | Gas turbine engine assembly and methods of assembling same |
US9145834B2 (en) | 2011-06-14 | 2015-09-29 | Honeywell International Inc. | Transverse mounted accessory gearbox |
US9926849B2 (en) | 2011-06-14 | 2018-03-27 | Honeywell International Inc. | Transverse mounted accessory gearbox |
US9062611B2 (en) * | 2011-10-19 | 2015-06-23 | United Technologies Corporation | Split accessory drive system |
US9140194B2 (en) * | 2012-01-11 | 2015-09-22 | Honeywell International Inc. | Gas turbine engine starter-generator with integrated lube oil scavenge functionality |
US9151224B2 (en) | 2012-03-14 | 2015-10-06 | United Technologies Corporation | Constant-speed pump system for engine thermal management system AOC reduction and environmental control system loss elimination |
US9121346B2 (en) | 2012-03-14 | 2015-09-01 | United Technologies Corporation | Pump system for TMS AOC reduction |
US9194294B2 (en) | 2012-05-07 | 2015-11-24 | United Technologies Corporation | Gas turbine engine oil tank |
JP5568596B2 (ja) * | 2012-05-30 | 2014-08-06 | 川崎重工業株式会社 | 航空機用エンジンのギヤボックス一体型発電装置 |
US10184404B2 (en) | 2012-09-20 | 2019-01-22 | United Technologies Corporation | Geared gas turbine engine accessory gearbox |
US9790861B2 (en) * | 2012-09-28 | 2017-10-17 | United Technologies Corporation | Gas turbine engine having support structure with swept leading edge |
US20140090386A1 (en) * | 2012-09-28 | 2014-04-03 | United Technologies Corporation | Geared turbofan with fan and core mounted accessory gearboxes |
US20140150440A1 (en) * | 2012-12-05 | 2014-06-05 | United Technologies Corporation | Gas turbine engine with a low speed spool driven pump arrangement |
US9297314B2 (en) * | 2012-12-19 | 2016-03-29 | United Technologies Corporation | Gas turbine engine with accessory gear box |
US9500133B2 (en) * | 2012-12-23 | 2016-11-22 | United Technologies Corporation | Mount with an axial upstream linkage for connecting a gearbox to a turbine engine case |
US10724479B2 (en) | 2013-03-15 | 2020-07-28 | United Technologies Corporation | Thrust efficient turbofan engine |
EP2971697B1 (de) * | 2013-03-15 | 2019-02-06 | United Technologies Corporation | Verteilter antrieb von triebwerk anbaugeräten |
US9624827B2 (en) * | 2013-03-15 | 2017-04-18 | United Technologies Corporation | Thrust efficient turbofan engine |
FR3007458B1 (fr) * | 2013-06-21 | 2017-11-10 | Snecma | Carter intermediaire ameliore de turbomachine et ensemble d'entrainement de boitier d'accessoire |
US20160160714A1 (en) * | 2013-09-26 | 2016-06-09 | United Technologies Corporation | Gas turbine engine with split lubrication system |
EP3063387B8 (de) * | 2013-11-01 | 2021-04-14 | Raytheon Technologies Corporation | Hilfsölpumpe für gasturbinenmotoruntersetzung |
US10746181B2 (en) * | 2016-08-22 | 2020-08-18 | Raytheon Technologies Corporation | Variable speed boost compressor for gas turbine engine cooling air supply |
US10823080B2 (en) | 2017-05-31 | 2020-11-03 | General Electric Company | Dual accessory gearbox |
US11168577B2 (en) * | 2018-10-24 | 2021-11-09 | Hamilton Sundstrand Corporation | Gearbox ratio change |
FR3110939B1 (fr) * | 2020-05-27 | 2022-09-09 | Safran Trans Systems | Turbomachine equipee de machines electriques accouplees a une surface d’accouplement |
DE102020117255A1 (de) | 2020-06-30 | 2021-12-30 | Rolls-Royce Deutschland Ltd & Co Kg | Gasturbinentriebwerk und Luftfahrzeug mit einem Gasturbinentriebwerk |
DE102020117254A1 (de) | 2020-06-30 | 2021-12-30 | Rolls-Royce Deutschland Ltd & Co Kg | Gasturbinentriebwerk und Luftfahrzeug mit einem Gasturbinentriebwerk |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
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US3806067A (en) | 1971-08-30 | 1974-04-23 | Gen Electric | Area ruled nacelle |
WO1995002120A1 (en) | 1993-07-06 | 1995-01-19 | Rolls-Royce Plc | Shaft power transfer in gas turbine engines |
US20050183423A1 (en) | 2004-02-25 | 2005-08-25 | Miller Guy W. | Apparatus for driving an accessory gearbox in a gas turbine engine |
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US2978869A (en) * | 1956-11-01 | 1961-04-11 | Bristol Siddeley Engines Ltd | Engine accessory mounting arrangements |
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DE3622022A1 (de) * | 1986-07-01 | 1988-01-07 | Kloeckner Humboldt Deutz Ag | Gasturbinentriebwerk |
GB2234035B (en) * | 1989-07-21 | 1993-05-12 | Rolls Royce Plc | A reduction gear assembly and a gas turbine engine |
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DE59701850D1 (de) * | 1996-04-30 | 2000-07-13 | Steyr Daimler Puch Ag | Verfahren zur feinregelung eines hydrostatisch-mechanischen leistungsverzweigungsgetriebes |
US5806805A (en) * | 1996-08-07 | 1998-09-15 | The Boeing Company | Fault tolerant actuation system for flight control actuators |
US6158210A (en) * | 1998-12-03 | 2000-12-12 | General Electric Company | Gear driven booster |
GB9910393D0 (en) * | 1999-05-05 | 1999-07-07 | Lucas Ind Plc | Electrical generator,an aero-engine including such a generator and an aircraft including such a generator |
FR2826052B1 (fr) * | 2001-06-19 | 2003-12-19 | Snecma Moteurs | Dispositif de secours au rallumage d'un turboreacteur en autorotation |
GB0128662D0 (en) * | 2001-11-30 | 2002-01-23 | Rolls Royce Plc | Improvements in or relating to generator arrangements |
GB0315894D0 (en) | 2003-07-08 | 2003-08-13 | Rolls Royce Plc | Aircraft engine arrangement |
FR2863312B1 (fr) * | 2003-12-09 | 2008-07-04 | Snecma Moteurs | Turboreacteur a double corps avec moyen d'entrainement des machines accessoires |
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-
2007
- 2007-11-14 US US11/939,725 patent/US8333554B2/en active Active
-
2008
- 2008-11-14 EP EP08253726.7A patent/EP2060759B1/de not_active Revoked
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
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US3806067A (en) | 1971-08-30 | 1974-04-23 | Gen Electric | Area ruled nacelle |
WO1995002120A1 (en) | 1993-07-06 | 1995-01-19 | Rolls-Royce Plc | Shaft power transfer in gas turbine engines |
US20050183423A1 (en) | 2004-02-25 | 2005-08-25 | Miller Guy W. | Apparatus for driving an accessory gearbox in a gas turbine engine |
Non-Patent Citations (2)
Title |
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RICHARD W. JOHNSON: "The Handbook of Fluid Dynamics", 1998, CRC PRESS LLC, ISBN: 3-540-64612-4, article DONALD J. DUSA, JAMES L. YOUNGHANS: "Nozzles and Diffusers", pages: 3pp, 42-1 - 42-4, XP055317217 |
ROLLS-ROYCE: "The Jet engine", 1986, ROLLS-ROYCE PLC, ISBN: 0902121235, article "Accessory drives", pages: 5pp, 65 - 71, XP055317209 |
Also Published As
Publication number | Publication date |
---|---|
US20090123274A1 (en) | 2009-05-14 |
EP2060759A2 (de) | 2009-05-20 |
EP2060759A3 (de) | 2012-03-21 |
US8333554B2 (en) | 2012-12-18 |
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